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Relevant bibliographies by topics / Satellite orbital motion model

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Academic literature on the topic 'Satellite orbital motion model'

Author: Grafiati

Published: 5 June 2025

Last updated: 15 July 2025

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Journal articles on the topic "Satellite orbital motion model"

1

Nakajima, Ayano, Shigeru Ida, and Yota Ishigaki. "Orbital evolution of Saturn’s satellites due to the interaction between the moons and the massive rings." Astronomy & Astrophysics 640 (August 2020): L15. http://dx.doi.org/10.1051/0004-6361/202038743.

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Context. Saturn’s mid-sized moons (satellites) have a puzzling orbital configuration with trapping in mean-motion resonances with every-other pairs (Mimas-Tethys 4:2 and Enceladus-Dione 2:1). To reproduce their current orbital configuration on the basis of a recent model of satellite formation from a hypothetical ancient massive ring, adjacent pairs must pass first-order mean-motion resonances without being trapped. Aims. The trapping could be avoided by fast orbital migration and/or excitation of the satellite’s eccentricity caused by gravitational interactions between the satellites and the

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Dubrovin, A. G., Yu N. Baranov, and A. P. Tryastsin. "The development of the model of satellite orbital motion." IOP Conference Series: Materials Science and Engineering 450 (December 4, 2018): 022033. http://dx.doi.org/10.1088/1757-899x/450/2/022033.

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Palkin, M. V., and I. P. Titkov. "Satellite Formation Flying Maneuver Control." Mekhatronika, Avtomatizatsiya, Upravlenie 20, no. 5 (2019): 308–13. http://dx.doi.org/10.17587/mau.20.308-313.

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A problem of a formation flying satellites maneuver control is presented. Among the most important criteria for satellite formation flying control system are active period maximization, precision of the configuration, secure motion (without collisions of satellites). Several methods for group configuration are presented: periodic impulse correction of each flying satellite position formation ("continuous order"); method of a satellite positioning on non-coplanar orbits ("variable order"). Other methods include combinations of methods mentioned above. Recommendations for their application are g

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MUNUSAMY, Raja, Kokila VASUDEVAN, and R. SUNDARAMOORTHY. "Design and Analysis of AAUSAT Cube Satellite Attitude Determination with PID Algorithms and Orbitron TLE." INCAS BULLETIN 15, no. 2 (2023): 49–57. http://dx.doi.org/10.13111/2066-8201.2023.15.2.5.

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Satellites are intended to be of massive cost, hard, or hard to keep up and fix in circle. The point of this task is to decide an effective strategy to decide the orbital and heading data for the Nano satellite. To design the exact trajectory and circle for a satellite, information regarding the components which are liable for the deviation in the method of satellites. The factors that should be taken into account to determine the exact location of the satellite. It could be accomplished with the assistance of software responsible for orbit simulation, to do programming with Orbitron so as to

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Shatina, A. V., M. I. Djioeva, and L. S. Osipova. "Mathematical Model of Satellite Rotation near Spin-Orbit Resonance 3:2." Nelineinaya Dinamika 18, no. 4 (2022): 0. http://dx.doi.org/10.20537/nd220803.

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This paper considers the rotational motion of a satellite equipped with flexible viscoelastic rods in an elliptic orbit. The satellite is modeled as a symmetric rigid body with a pair of flexible viscoelastic rods rigidly attached to it along the axis of symmetry. A planar case is studied, i. e., it is assumed that the satellite’s center of mass moves in a Keplerian elliptic orbit lying in a stationary plane and the satellite’s axis of rotation is orthogonal to this plane. When the rods are not deformed, the satellite’s principal central moments of inertia are equal to each other. The linear b

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Gorchakov, S. Yu. "Mathematical modeling of velocity and accelerations fields of image motion in the optical equipment of the Earth remote sensing satellite." Russian Technological Journal 11, no. 6 (2023): 47–56. http://dx.doi.org/10.32362/2500-316x-2023-11-6-47-56.

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Objectives. The paper considers a satellite with an optoelectronic payload designed to take pictures of the Earth’s surface. The work sets out to develop a mathematical model for determining the dependencies between the state vector of the satellite, the state vector of the point being imaged on the Earth’s surface, and the distribution fields of the velocity vectors and accelerations of the motion of the image along the focal plane of the optoelectronic payload.Methods. The method is based on double differentiation of the photogrammetry equation when applied to a survey of the Earth’s surface

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Yoon, Yihun, Woojae Jang, and Jintai Chung. "Natural Frequencies of a Tethered Satellite System." Applied Sciences 15, no. 4 (2025): 2180. https://doi.org/10.3390/app15042180.

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This study investigated the natural frequencies of a tethered satellite system to enhance stability and operational reliability. Tethered satellite systems provide many advantages for space missions but exhibit inherently complex dynamics due to the interaction between rigid-body motions and tether deformation. A dumbbell model was employed to analyze rigid-body dynamics, with eigenvalue analysis used to determine the natural frequencies of orbital and librational motion. Additionally, tether deformation was examined through simulations based on the absolute nodal coordinate formulation (ANCF)

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Kudryavtsev, Sergey M. "New semi-analytical calculation of lunar, solar and planetary perturbations in motion of Earth satellites." Proceedings of the International Astronomical Union 18, S382 (2022): 142–45. http://dx.doi.org/10.1017/s1743921323003988.

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AbstractWe suggest an advanced algorithm for semi-analytical calculation of orbital perturbations of Earth artificial satellites caused by the gravity attraction of the “3rd-bodies” (the Moon, the Sun, major planets). A new accurate analytical series for the relevant perturbation function is developed. It is obtained through a careful spectral analysis of the long-term DE406 planetary/lunar ephemerides and valid over 2000 years, 1000-3000. The series is used in the author’s semi-analytical model of satellite motion. The results of the motion prediction of several Earth satellites obtained by m

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Chernikova, Oksana Sergeevna, and Yuliya Sergeevna Chetvertakova. "Two-stage parametric identification procedure to predict satellite orbital motion." International Journal of Electrical and Computer Engineering (IJECE) 12, no. 5 (2022): 5348. http://dx.doi.org/10.11591/ijece.v12i5.pp5348-5354.

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<span>The paper presents a new step-by-step procedure for constructing a navigation satellite motion model. At the first stage of the procedure, the parameters of the radiation pressure model are estimated using the maximum likelihood method. The statistic estimator based on the continuous-discrete adaptive unscented Kalman filter is proposed for the solar radiation model parameters estimation. Step-by-step scheme of filtering algorithm used for the software development are given. At the second stage, the parameters of the unaccounted perturbations model are estimated based on the result

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Yakovlev, O. Ya, and D. V. Malygin. "External thermal modeling satellite platform «Synergy»." Spacecrafts & Technologies 3, no. 3 (2019): 155–63. http://dx.doi.org/10.26732/2618-7957-2019-3-155-163.

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In order to conduct thermal research of the satellite platform «Synergy», a mathematical model has been developed for calculating external thermal loads for spacecraft of the CubeSat form factor, operating in various orientation modes in near-Earth circular orbits. When modeling thermal conditions, heat fluxes from the Sun, the earth's flux and atmospheric effects are taken into account. A feature of the model is the transition to a moving geocentric coordinate system for determining the density of heat fluxes of direct and reflected solar radiation. The study of thermal conditions in the proc

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Dissertations / Theses on the topic "Satellite orbital motion model"

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Snider, James Ralph. "Satellite motion around an oblate planet: a perturbation solution for all orbital parameters." Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/26751.

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Panzetta, Francesca. "Determination of the ocean tide model from LEO satellite orbital perturbation analysis." Doctoral thesis, Università degli studi di Padova, 2013. http://hdl.handle.net/11577/3423424.

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The present study concerns the determination of ocean tide model parameters from GOCE orbital perturbation analysis. The GOCE satellite was launched by the European Space Agency in 2009 and is flying on a Sun-synchronous near circular orbit, at the very low altitude of about 250 km which makes it very sensitive to tidally induced orbit perturbations. The strategy adopted for analyzing GOCE GPS tracking data is the direct fully-dynamic approach, consisting in the GOCE precise orbit determination (POD) and accumulation of the normal equations for each orbital arc, followed by a multiarc so

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Rogers, Andrew Charles. "Optimization-Based Guidance for Satellite Relative Motion." Diss., Virginia Tech, 2016. http://hdl.handle.net/10919/79455.

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Spacecraft relative motion modeling and control promises to enable or augment a wide range of missions for scientific research, military applications, and space situational awareness. This dissertation focuses on the development of novel, optimization-based, control design for some representative relative-motion-enabled missions. Spacecraft relative motion refers to two (or more) satellites in nearly identical orbits. We examine control design for relative configurations on the scale of meters (for the purposes of proximity operations) as well as on the scale of tens of kilometers (representat

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Phipps, Warren E. Jr. "Parallelization of the Naval Space Surveillance Center (NAVSPASUR) satellite motion model." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/24001.

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Approved for public release; distribution is unlimited<br>The Naval Space Surveillance Center (NAVSPASUR) uses an analytic satellite motion model based on the Brouwer-Lyddane theory to assist in tracking over 6000 objects in orbit around the earth. The satellite motion model is implemented by a Fortran subroutine, PPT2. Due to the increasing number of objects required to be tracked, NAVSPASUR desires a method to reduce the computation time of this satellite motion model. Parallel computing offers one method to achieve this objective. This thesis investigates the parallel computing potenti

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Акуленко, Л. Д., Д. Д. Лещенко та Т. А. Козаченко. "Движения твердого тела, близкие к случаю Лагранжа". Thesis, Сумский государственный университет, 2017. http://essuir.sumdu.edu.ua/handle/123456789/65372.

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В работе исследуется возмущенное движение относительно неподвижной точки динамически симметричного тяжелого твердого тела под действием момента сил произвольной природы. Момент силы тяжести не рассматривается как возмущающий момент, а относится к невозмущенному движению, которое представляет собой движение в случае Лагранжа.

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Oumer, Nassir Workicho. "Visual Tracking and Motion Estimation for an On-orbit Servicing of a Satellite." Doctoral thesis, 2016. https://repositorium.ub.uni-osnabrueck.de/handle/urn:nbn:de:gbv:700-2016092815002.

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This thesis addresses visual tracking of a non-cooperative as well as a partially cooperative satellite, to enable close-range rendezvous between a servicer and a target satellite. Visual tracking and estimation of relative motion between a servicer and a target satellite are critical abilities for rendezvous and proximity operation such as repairing and deorbiting. For this purpose, Lidar has been widely employed in cooperative rendezvous and docking missions. Despite its robustness to harsh space illumination, Lidar has high weight and rotating parts and consumes more power, thus undermines

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(11014071), Vivek Muralidharan. "Stretching Directions in Cislunar Space: Stationkeeping and an application to Transfer Trajectory Design." Thesis, 2021.

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<div>The orbits of interest for potential missions are stable or nearly stable to maintain long term presence for conducting scientific studies and to reduce the possibility of rapid departure. Near Rectilinear Halo Orbits (NRHOs) offer such stable or nearly stable orbits that are defined as part of the L1 and L2 halo orbit families in the circular restricted three-body problem. Within the Earth-Moon regime, the L1 and L2 NRHOs are proposed as long horizon trajectories for cislunar exploration missions, including NASA's upcoming Gateway mission. These stable or nearly stable orbits do not poss

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Books on the topic "Satellite orbital motion model"

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Reilly, Charles H. A satellite system synthesis model for orbital arc allotment optimization. National Aeronautics and Space Administration, Lewis Research Center, 1987.

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2

Scheeres, Daniel J. Orbital motion in strongly perturbed environments: Applications to asteroid, comet and planetary satellite orbiters. Springer, 2012.

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3

Danielson, D. A. Satellite motion around an oblate planet: A perturbation solution for all orbital parameters. Naval Postgraduate School, 1993.

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4

Snider, James Ralph. Satellite motion around an oblate planet: A perturbation solution for all orbital parameters. Naval Postgraduate School, 1989.

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5

Dilley, A. C. Improved AVHRR data navigation using automated land feature recognition to correct a satellite orbital model. Commonwealth Scientific and Industrial Research Organization, 1994.

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6

Phipps, Warren E. Paralellization of the Naval Space Surveillance Center (NAVSPASUR) satellite motion model. Naval Postgraduate School, 1992.

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7

J, Bourassa Roger, Gruenbaum P. E, and Langley Research Center, eds. Operation of the computer model for microenvironment solar exposure. National Aeronautics and Space Administration, Langley Research Center, 1995.

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Scheeres, Daniel J. Orbital Motion in Strongly Perturbed Environments: Applications to Asteroid, Comet and Planetary Satellite Orbiters. Springer Berlin / Heidelberg, 2014.

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Scheeres, Daniel J. Orbital Motion in Strongly Perturbed Environments: Applications to Asteroid, Comet and Planetary Satellite Orbiters. Springer, 2012.

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10

Hu, Xuhui. Introduction. Oxford University Press, 2018. http://dx.doi.org/10.1093/oso/9780198808466.003.0001.

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This chapter firstly introduces the broad theoretical background within which the research carried out in this book is situated. The theoretical aim of this book is to develop a theory of the syntax of events, which is based on the constructivist approach, in particular Borer’s (2005a,b, 2013) Exo-Skeletal (XS) model—part of the broader framework of generative grammar. The empirical scope of this book includes Chinese and English resultatives, applicative constructions, non-canonical object constructions and motion event constructions in Chinese, and the satellite/verb-framed typology. Both sy

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Book chapters on the topic "Satellite orbital motion model"

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Kéchichian, Jean Albert. "The Mathematical Models of the Jet Propulsion Laboratory (JPL) Artificial Satellite Analysis Program (ASAP)." In Orbital Relative Motion and Terminal Rendezvous. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-64657-8_12.

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Yan, Ye, Xu Huang, and Yueneng Yang. "Dynamical Model of Lorentz-Augmented Orbital Motion." In Dynamics and Control of Lorentz-Augmented Spacecraft Relative Motion. Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-2603-4_2.

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Broucke, R., and A. Konopliv. "Some Models for the Motion of the Co-orbital Satellites of Saturn." In Long-Term Dynamical Behaviour of Natural and Artificial N-Body Systems. Springer Netherlands, 1988. http://dx.doi.org/10.1007/978-94-009-3053-7_12.

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Exertier, P., G. Metris, Y. Boudon, and F. Barlier. "Mean Orbital Motion of Lageos Satellite Derived from Laser Ranging Observations." In Geodesy and Physics of the Earth. Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-78149-0_29.

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Liu, Lin. "Analytical Non-singularity Perturbation Solutions for Extrapolation of Earth’s Satellite Orbital Motion." In Springer Series in Astrophysics and Cosmology. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-4839-8_4.

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Joshi, Amitabh. "On the nonlinear orbital motion of the driven two-photon Jaynes-Cummings model." In Coherence and Quantum Optics VIII. Springer US, 2003. http://dx.doi.org/10.1007/978-1-4419-8907-9_100.

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Wang, Zhiwen, Hui Xu, Qianxin Wang, and Yilei He. "A Method for Polar Motion Prediction Based on LS Model of Error Compensation." In China Satellite Navigation Conference (CSNC) 2017 Proceedings: Volume III. Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-4594-3_8.

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Kinoshita, Hiroshi. "Motion of the Orbital Plane of a Satellite Due to a Secular Change of the Obliquity of its Mother Planet." In Interactions Between Physics and Dynamics of Solar System Bodies. Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-011-1902-3_29.

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Huntley, David, Drew Rotheram-Clarke, Roger MacLeod, Robert Cocking, Jamel Joseph, and Philip LeSueur. "Landslide Monitoring with RADARSAT Constellation Mission InSAR, RPAS-Derived Point-Clouds and RTK-GNSS Time-Series in the Thompson River Valley, British Columbia, Canada." In Progress in Landslide Research and Technology, Volume 2 Issue 1, 2023. Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-39012-8_19.

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AbstractIn this paper, we evaluate the effectiveness of four land-deformation measurement techniques for monitoring slow-moving landslides along a high-risk section of the national railway corridor traversing the Thompson River valley, British Columbia, Canada. The geomorphically active North Slide acts as an ideal field laboratory for testing and evaluating novel monitoring techniques and methods. We compare differential processing of Structure from Motion (SfM) products such as point-cloud elevation models and orthophotos derived from Remotely Piloted Aircraft Systems (RPAS), along with satellite based Interferometric Synthetic Aperture Radar (InSAR) deformation measurements derived from RADARSAT Constellation Mission (RCM). These results are ground-truthed with periodic real-time kinematic (RTK) global navigation satellite system (GNSS) measurements. We evaluate point-cloud comparison techniques, including the multi-scale model-to-model cloud comparison (M3C2) algorithm and digital ortho image correlation techniques. Multi-temporal RCM InSAR deformation measurements are processed using a semi-automated processing system for interferogram generation and unwrapping. Manual processing of small baseline subsets (SBAS) leads to the recovery of 1-dimensional line-of-sight (LoS) and 2-dimensional deformation measurements. Lastly, we discuss the strengths and limitations of these techniques, considerations for interpreting their outputs, and considerations for direct comparisons between InSAR, RPAS and RTK-GNSS deformation measurements.

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Guerrini, Federica. "Data-Informed Models for the Coupled Dispersal of Microplastics and Related Pollutants Applied to the Mediterranean Sea." In Special Topics in Information Technology. Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-15374-7_1.

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AbstractMicroplastic pollution is a ubiquitous environmental threat, in particular to the oceans. In the marine environment, microplastics are not just passively transported by sea currents, but often get contaminated with organic pollutants during the journey. The uptake of chemicals onto microplastics can worsen the adverse effects of microplastics to marine organisms; however, investigation on this urgent phenomenon is hampered by the impossibility of monitoring and tracking such small plastic fragments during their motion at sea. This work aims at addressing the need for an effective modelling of the advection–diffusion processes jointly involving microplastics and the pollutants they carry to further our understanding of their spatiotemporal patterns and ecological impacts, focusing on the Mediterranean Sea. Here we present the conceptual design, methodological settings, and modelling results of a novel, data-informed 2D Lagrangian–Eulerian modelling framework that simultaneously describes (i) the Lagrangian dispersal of microplastic on the sea surface, (ii) the Eulerian advection–diffusion of selected organic contaminants, and (iii) the gradient-driven chemical exchanges between microplastic particles and chemical pollutants in the marine environment in a simple, yet comprehensive way. Crucial to the realism of our model is exploiting the wide variety and abundance of data linked with drivers of Mediterranean marine pollution by microplastics and chemicals, ranging from national censuses to satellite data of surface water runoff and GPS ship tracking, other than the use of oceanographic reanalyses to inform microplastics’ motion at sea. The results of our method applied to a multi-year simulation contribute to a first basin-wide assessment of the role of microplastics as a vehicle of other pollutants of concern in the marine environment. The framework proposed here is intended as a flexible tool to help advance knowledge towards a comprehensive description of the multifaceted threat of marine plastic pollution and an informed support to targeted mitigation policies.

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Conference papers on the topic "Satellite orbital motion model"

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Kim, Junsik, Yuna Choi, Youngjin Choi, et al. "Axis Kinematics Algorithm for Satellite Manipulator System in Orbital Motion." In 2024 International Conference on Space Robotics (iSpaRo). IEEE, 2024. http://dx.doi.org/10.1109/isparo60631.2024.10687540.

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Lv, Chongyu, Sheng Fang, Boyu Hua, et al. "Buoy Loss Model for Satellite-to-sea Communication Cooperating 6D Motion." In 2024 Photonics & Electromagnetics Research Symposium (PIERS). IEEE, 2024. http://dx.doi.org/10.1109/piers62282.2024.10618358.

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Alesia Herasimenka, Miss, Ariadna Farrés, and Lamberto Dell'Elce. "Station-keeping under conical constraint on the control force." In ESA 12th International Conference on Guidance Navigation and Control and 9th International Conference on Astrodynamics Tools and Techniques. ESA, 2023. http://dx.doi.org/10.5270/esa-gnc-icatt-2023-082.

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Due to specific mission goals, many satellites are subject to cone constraints on the thrust direction. For example, James Webb Space Telescope, launched on December 25, 2021 toward a Halo orbit around the Sun-Earth L2 libration point, has a thermal shield that must prevent the telescope and other instruments from overheating [1]. Therefore, it is constrained to always keep its attitude such that the angle between the normal to the shield and the Sun direction is smaller than 53 deg. It results in conical constraints for the propulsion directions. Using chemical propulsion to perform small imp

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Mankala, Kalyan K., and Sunil K. Agrawal. "Dynamic Modeling and Simulation of Impact in Tether Net/Gripper Systems." In ASME 2003 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/detc2003/vib-48505.

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The objective of this paper is to study the dynamic modeling and simulation of a tether-net/gripper system during an impact, while it is being deployed or retrieved by a winch on a satellite orbiting around earth. We stick to Tether-Net system but the analysis is applicable to Tether-Gripper systems too. We assume that the net is deployed from the satellite in orbit and the motion is restricted to the orbital plane. This net captures a second satellite and tows it. The motion of a tether-net system can be broken down into the following phases: (i) Phase 1: Net is shot out from the satellite wi

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Mankala, Kalyan K., and Sunil K. Agrawal. "Dynamic Modeling and Simulation of Satellite Tethered Systems." In ASME 2003 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/detc2003/vib-48344.

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The objective of this paper is to study the dynamic simulation of a tether as it is deployed or retrieved by a winch on a satellite orbiting around earth. In an effort to understand the problem incrementally, the following three models were developed: (a) Model 1: A tether with constant length moves on earth in the plane of constant gravity; (b) Model 2: A tether is deployed from a drum on earth in the plane of constant gravity, i.e., length of the cable changes during deployment; (c) Model 3: A tether is deployed from a drum on an orbiting satellite. These models have been chosen to bring dif

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Aliberti, Stefano, Marco B. Quadrelli, and Marcello Romano. "Dynamics and Aerodynamic Control of a Cross-Track Tether Satellite System." In ESA 12th International Conference on Guidance Navigation and Control and 9th International Conference on Astrodynamics Tools and Techniques. ESA, 2023. http://dx.doi.org/10.5270/esa-gnc-icatt-2023-098.

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The objective of this paper is to present and analyze the dynamics and control strategy of a novel type of formation flight architecture, that could enable unprecedented space mission capabilities. In particular we propose and study a tether satellite system composed by two or more satellites, flying in LEO, connected by a linear tether. That tether is maintained in tension along the cross-track direction, with respect to the orbit, i.e., perpendicular to the motion and radial directions, by exploiting the aerodynamic lift acting upon the suitably oriented satellites. Possible applications of

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Terui, Fuyuto, Heihachiro Kamimura, and Shin' ichiro Nishida. "Motion Estimation to a Failed Satellite on Orbit using Stereo Vision and 3D Model Matching." In 2006 9th International Conference on Control, Automation, Robotics and Vision. IEEE, 2006. http://dx.doi.org/10.1109/icarcv.2006.345305.

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Babanin, Alexander V. "Swell Attenuation due to Wave-Induced Turbulence." In ASME 2012 31st International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/omae2012-83706.

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In the paper, we will discuss two separate, but connected issues: wave-turbulence interactions, and estimates of swell attenuation due to such turbulence. Theoreticaly, potential waves cannot generate the vortex motion, but the scale considerations indicate that if the steepness of waves is not too small, the Reynolds number can exceed the critical values. This means that in presence of initial non-potential disturbances the orbital velocities can generate the vortex motion and turbulence. This problem was investigated by laboratory means, numerical simulations and field observations. As a sin

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Casu, Davide, Vincent Dubanchet, Hervé Renault, Anthea Comellini, and Pierre Dandré. "EROSS+ Phase A/B1 Guidance, Navigation and Control design for In-Orbit Servicing." In ESA 12th International Conference on Guidance Navigation and Control and 9th International Conference on Astrodynamics Tools and Techniques. ESA, 2023. http://dx.doi.org/10.5270/esa-gnc-icatt-2023-036.

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The H2020 project “EROSS+ Phase A/B1” standing for “European Robotic Orbital Support Services” has been over 2021-2023 to mature the future robotic servicing missions with a highly-autonomous and coupled Guidance, Navigation and Control (GNC) architecture for both a satellite platform and its embedded robotic arm. This project is built upon the previous developments of the Operational Grants led by the Strategic Research Cluster in Space Robotics funded by the European Commission since 2016. More specifically, EROSS+ project aims at deriving a system design of a robotic Servicer approaching, c

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Lampariello, Roberto, and Gerhard Hirzinger. "Modeling and Experimental Design for the On-Orbit Inertial Parameter Identification of Free-Flying Space Robots." In ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/detc2005-85242.

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A method is proposed for the identification of the inertial parameters of a free-flying robot directly in orbit, using accelerometers. This can serve to improve the path planning and tracking capabilities of the robot, as well as its efficiency in energy consumption. The method is applied to the identification of the base body and of the load on the end-effector, giving emphasis to the experimental design. The problem of the identification of the full system is also addressed in its theoretical aspects. The experience from the Getex Dynamic Motion experiments performed on the ETS-VII satellite

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Reports on the topic "Satellite orbital motion model"

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Danielson, D. A., G. E. Latta, C. P. Sagovac, S. D. Krambeck, and J. R. Snider. Satellite Motion Around an Oblate Planet: A Perturbation Solution for All Orbital Parameters. Defense Technical Information Center, 1993. http://dx.doi.org/10.21236/ada265779.

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Phipps, Jr, Neta Warren E., Danielson Beny, and D. A. Parallelization of the Naval Space Surveillance Satellite Motion Model. Defense Technical Information Center, 1993. http://dx.doi.org/10.21236/ada531142.

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Beason, Scott, Taylor Kenyon, Robert Jost, and Laurent Walker. Changes in glacier extents and estimated changes in glacial volume at Mount Rainier National Park, Washington, USA from 1896 to 2021. National Park Service, 2023. http://dx.doi.org/10.36967/2299328.

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Surface area of glaciers and perennial snow within Mount Rainier National Park were delineated based on 2021 aerial Structure-from-Motion (SfM) and satellite imagery to document changes to glaciers over the last 125 years. These extents were compared with previously completed databases from 1896, 1913, 1971, 1994, 2009, and 2015. In addition to the glacial features mapped at the Park, any snow patches noted in satellite- and fixed-wing- acquired aerial images in September 2021 were mapped as perennial snowfields. In 2021, Mount Rainier National Park contained a total of 28 named glaciers which

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